GIII BL0 AIRFOIL (giiia-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL0 AIRFOIL (giiia-il) Reynolds number: 100,000 Max Cl/Cd: 38.88 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiia-il-100000-n5.txt Download as CSV file: xf-giiia-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6842 0.08436 0.07940 -0.0219 1.0000 0.0237
-11.000 -0.7035 0.07659 0.07155 -0.0274 1.0000 0.0235
-10.750 -0.7245 0.07031 0.06515 -0.0310 1.0000 0.0233
-10.500 -0.7456 0.06523 0.05991 -0.0322 1.0000 0.0232
-10.250 -0.7658 0.06097 0.05546 -0.0314 1.0000 0.0232
-10.000 -0.7846 0.05724 0.05151 -0.0289 1.0000 0.0232
-9.750 -0.7996 0.05361 0.04759 -0.0259 1.0000 0.0233
-9.500 -0.8094 0.04993 0.04353 -0.0228 1.0000 0.0234
-9.250 -0.8143 0.04648 0.03965 -0.0197 1.0000 0.0236
-9.000 -0.8145 0.04299 0.03588 -0.0170 1.0000 0.0242
-8.750 -0.8069 0.04088 0.03363 -0.0150 1.0000 0.0252
-8.500 -0.7966 0.03926 0.03183 -0.0130 1.0000 0.0266
-8.250 -0.7859 0.03732 0.02963 -0.0108 1.0000 0.0282
-8.000 -0.7746 0.03495 0.02688 -0.0083 1.0000 0.0295
-7.750 -0.7607 0.03260 0.02413 -0.0061 1.0000 0.0306
-7.500 -0.7441 0.03059 0.02174 -0.0041 1.0000 0.0319
-7.250 -0.7275 0.02877 0.01974 -0.0024 1.0000 0.0341
-7.000 -0.7108 0.02760 0.01849 -0.0007 1.0000 0.0367
-6.750 -0.6923 0.02629 0.01702 0.0010 1.0000 0.0391
-6.500 -0.6733 0.02499 0.01554 0.0027 1.0000 0.0415
-6.250 -0.6553 0.02384 0.01427 0.0045 1.0000 0.0446
-6.000 -0.6393 0.02290 0.01335 0.0064 1.0000 0.0489
-5.750 -0.6225 0.02202 0.01238 0.0084 1.0000 0.0532
-5.500 -0.6069 0.02111 0.01141 0.0107 1.0000 0.0575
-5.250 -0.5911 0.02042 0.01068 0.0127 1.0000 0.0651
-5.000 -0.5756 0.01968 0.00996 0.0149 1.0000 0.0738
-4.750 -0.5598 0.01900 0.00930 0.0170 1.0000 0.0858
-4.500 -0.5436 0.01836 0.00876 0.0190 1.0000 0.1061
-4.250 -0.5273 0.01776 0.00829 0.0209 1.0000 0.1338
-4.000 -0.5104 0.01720 0.00790 0.0227 1.0000 0.1719
-3.750 -0.4933 0.01667 0.00750 0.0244 1.0000 0.2157
-3.500 -0.4748 0.01601 0.00711 0.0257 0.9994 0.2754
-3.250 -0.4510 0.01444 0.00679 0.0257 0.9938 0.4987
-3.000 -0.4211 0.01392 0.00696 0.0260 0.9885 0.6815
-2.750 -0.3818 0.01402 0.00725 0.0248 0.9849 0.7674
-2.500 -0.3420 0.01429 0.00752 0.0233 0.9799 0.8158
-2.250 -0.3005 0.01457 0.00770 0.0211 0.9751 0.8484
-2.000 -0.2579 0.01486 0.00786 0.0187 0.9698 0.8703
-1.750 -0.2146 0.01510 0.00797 0.0159 0.9644 0.8885
-1.500 -0.1691 0.01534 0.00809 0.0127 0.9593 0.9038
-1.250 -0.1206 0.01559 0.00826 0.0090 0.9540 0.9173
-1.000 -0.0677 0.01573 0.00832 0.0041 0.9495 0.9265
-0.750 -0.0278 0.01569 0.00820 0.0016 0.9388 0.9350
-0.500 0.0196 0.01554 0.00798 -0.0024 0.9256 0.9376
-0.250 0.0641 0.01532 0.00770 -0.0055 0.9073 0.9410
0.000 0.0995 0.01514 0.00745 -0.0067 0.8841 0.9471
0.250 0.1358 0.01494 0.00718 -0.0080 0.8582 0.9519
0.500 0.1705 0.01478 0.00695 -0.0091 0.8314 0.9573
0.750 0.2011 0.01467 0.00677 -0.0094 0.8017 0.9640
1.000 0.2351 0.01454 0.00658 -0.0105 0.7645 0.9693
1.250 0.2663 0.01445 0.00637 -0.0109 0.7240 0.9755
1.500 0.3008 0.01439 0.00613 -0.0121 0.6862 0.9802
1.750 0.3331 0.01442 0.00602 -0.0130 0.6489 0.9858
2.000 0.3676 0.01447 0.00591 -0.0144 0.6104 0.9903
2.250 0.4010 0.01458 0.00586 -0.0157 0.5719 0.9952
2.500 0.4354 0.01469 0.00585 -0.0173 0.5314 0.9997
2.750 0.4584 0.01486 0.00590 -0.0166 0.4942 1.0000
3.000 0.4803 0.01507 0.00597 -0.0157 0.4517 1.0000
3.250 0.5017 0.01535 0.00607 -0.0147 0.3991 1.0000
3.500 0.5226 0.01576 0.00623 -0.0137 0.3493 1.0000
3.750 0.5437 0.01617 0.00645 -0.0128 0.3104 1.0000
4.000 0.5649 0.01656 0.00672 -0.0119 0.2851 1.0000
4.250 0.5860 0.01695 0.00702 -0.0109 0.2694 1.0000
4.500 0.6071 0.01733 0.00738 -0.0099 0.2587 1.0000
4.750 0.6279 0.01774 0.00778 -0.0088 0.2510 1.0000
5.000 0.6491 0.01811 0.00820 -0.0078 0.2441 1.0000
5.250 0.6699 0.01855 0.00864 -0.0066 0.2387 1.0000
5.500 0.6911 0.01896 0.00912 -0.0056 0.2334 1.0000
5.750 0.7123 0.01939 0.00965 -0.0045 0.2281 1.0000
6.000 0.7333 0.01990 0.01017 -0.0034 0.2239 1.0000
6.250 0.7550 0.02039 0.01078 -0.0023 0.2204 1.0000
6.500 0.7766 0.02087 0.01141 -0.0013 0.2162 1.0000
6.750 0.7962 0.02136 0.01191 0.0000 0.2076 1.0000
7.000 0.8130 0.02160 0.01230 0.0016 0.1920 1.0000
7.250 0.8296 0.02178 0.01262 0.0033 0.1744 1.0000
7.500 0.8472 0.02201 0.01300 0.0049 0.1577 1.0000
7.750 0.8651 0.02225 0.01337 0.0064 0.1374 1.0000
8.250 0.8890 0.02457 0.01515 0.0108 0.0486 1.0000
8.500 0.8993 0.02597 0.01661 0.0134 0.0408 1.0000
8.750 0.9094 0.02726 0.01806 0.0160 0.0359 1.0000
9.000 0.9188 0.02849 0.01944 0.0185 0.0320 1.0000
9.250 0.9234 0.03000 0.02106 0.0216 0.0297 1.0000
9.500 0.9276 0.03146 0.02265 0.0248 0.0284 1.0000
9.750 0.9331 0.03282 0.02419 0.0277 0.0272 1.0000
10.000 0.9375 0.03425 0.02579 0.0306 0.0259 1.0000
10.250 0.9405 0.03572 0.02739 0.0335 0.0245 1.0000
10.500 0.9408 0.03722 0.02899 0.0365 0.0232 1.0000
10.750 0.9401 0.03894 0.03079 0.0391 0.0222 1.0000
11.000 0.9382 0.04105 0.03297 0.0413 0.0213 1.0000
11.250 0.9379 0.04354 0.03554 0.0432 0.0207 1.0000
11.500 0.9399 0.04579 0.03799 0.0446 0.0203 1.0000
11.750 0.9404 0.04831 0.04072 0.0457 0.0200 1.0000
12.000 0.9388 0.05115 0.04382 0.0464 0.0197 1.0000
12.250 0.9349 0.05434 0.04724 0.0467 0.0194 1.0000
12.500 0.9285 0.05798 0.05110 0.0463 0.0192 1.0000
12.750 0.9198 0.06212 0.05546 0.0452 0.0191 1.0000
13.000 0.9088 0.06683 0.06039 0.0433 0.0190 1.0000
13.250 0.8958 0.07219 0.06595 0.0407 0.0190 1.0000
13.500 0.8807 0.07821 0.07217 0.0372 0.0190 1.0000
13.750 0.8639 0.08497 0.07911 0.0331 0.0191 1.0000
14.000 0.8453 0.09248 0.08679 0.0285 0.0192 1.0000
14.250 0.8255 0.10077 0.09522 0.0233 0.0194 1.0000
14.500 0.8045 0.10982 0.10434 0.0179 0.0196 1.0000
14.750 0.7830 0.11951 0.11411 0.0124 0.0199 1.0000
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